EP2665910A1 - Fluggasturbinenschubumkehrvorrichtung - Google Patents
FluggasturbinenschubumkehrvorrichtungInfo
- Publication number
- EP2665910A1 EP2665910A1 EP12700788.8A EP12700788A EP2665910A1 EP 2665910 A1 EP2665910 A1 EP 2665910A1 EP 12700788 A EP12700788 A EP 12700788A EP 2665910 A1 EP2665910 A1 EP 2665910A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- engine
- thrust
- elements
- cowling
- deflecting
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
- F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
- F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
- F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/76—Control or regulation of thrust reversers
- F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
Definitions
- the invention relates to an aircraft gas turbine thrust reverser with an engine, with an engine cowling and with several, arranged on the peripheral region, variable position deflecting elements.
- a thrust reverser in which deflection elements or flow guide elements are provided in a bypass duct through which air is passed from a fan, which from a forward thrust position, in which the flow of the bypass channel can take place unhindered in a Thrust reversing position are movable.
- the geometry of the bypass channel and in particular the geometry of the lining of the core engine is given in a substantially axial displacement of the thrust reverser either an adjustment of the geometry of the bypass channel or not completely closing the bypass channel.
- the US 2009/0301056 A1 shows a construction in which the deflecting elements or flow guide elements are moved in a straight line at an angle to the axial axis of the engine. Again, it is necessary to modify the geometry of the lining of the core engine so that a complete flow diversion can take place. This results in disadvantages in terms of performance in forward thrust operation.
- the object of the invention is to provide an aircraft gas turbine thrust reverser of the type mentioned in the introduction which has a high degree of efficiency with a simple construction and simple, cost-effective manufacturability and can be used for different geometries of aircraft gas turbines.
- the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.
- the rear region of the engine cowling in the axial direction of the engine is displaceable from a closed forward thrust position to a thrust reverse position displaced to the rear, in which a substantially annular free space results to a front, fixed region of the engine cowling.
- the clearance makes it possible to move deflectors in the displacement of the rear portion of the engine cowling on a pointing to the central axis of the engine pitch circle track in the free space.
- the rear portion of the engine cowling is axially displaced while the baffles are displaced on an arcuate path or part-circular path.
- an arcuate or part-circular path is understood to mean a curved or rounded path which is also formed with a complex structure but in any case is not straight.
- the baffles enter the bypass duct and redirect the flow in the bypass duct to thrust reversal.
- the deflecting elements can be applied with their rear end region in contact with a lining of the core engine.
- the deflection lead to a seal and blockage of the bypass channel.
- the deflection thus lead by their (in the radial direction) height to a seal and blockage of the bypass channel, so that only a relatively small additional blockage element is required.
- the rear portion of the engine cowling may be integrally formed and have a substantially annular shape. This circular ring shape is interrupted only by a recess, which is needed for mounting the pylon for suspension of the engine.
- the deflecting elements are moved on a circular arcuate or part-circular path. It is particularly advantageous if the deflecting elements are mounted and guided by means of rail elements. These rail elements can be accommodated in the front region of the engine cowling without obstructing the flow through the bypass duct becomes. Even in the thrust reversing position, there are no flow disturbing components in the bypass duct.
- This blockage of flow through the bypass duct may occur at a location where the radial diameter of the engine cowl of the core engine reaches its maximum. This enables the axial movement of the slidable rear portion of the engine cowling to be reduced. This results according to the invention the possibility to use smaller and lighter actuation and drive devices.
- the leading edge of the rear portion of the panel is part-circular or curved and not straight.
- the trajectory of both the baffles and the rear portion of the panel is preferably arcuate or formed in a similar complex structure to optimize the kinematics and effectively utilize the available clearance.
- a plurality of guide elements is preferably formed on the deflecting element, wherein the deflecting element is configured overall preferably in the manner of a grid. This results in a stable construction, which flow-optimized. This is achieved in particular by a cascade-shaped design of the deflecting element.
- the individual deflecting elements are spaced apart from one another in the forward thrust position in the circumferential direction and are arranged approximately in the thrust reversing position with respect to one another.
- the individual deflecting elements are spaced apart from one another in the forward thrust position in the circumferential direction and are arranged approximately in the thrust reversing position with respect to one another.
- FIG. 1 is a schematic representation of a gas turbine engine according to the present invention
- FIGS. 2 and 3 5 perspective views obliquely from behind the aircraft gas turbine according to FIGS. 2 and 3 in the forward thrust position or thrust reversing position,
- Fig. 6 is a schematic partial sectional view for explaining the
- Fig. 7 is a partial perspective view of the invention
- Fig. 8 is a perspective view, analogous to FIG. 7, in the forward thrust position.
- FIG. 9, 10 are perspective views of the deflecting element according to the invention.
- the gas turbine engine 10 of FIG. 1 is an example of a turbomachine to which the invention may apply. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
- the engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.
- the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
- the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of the high pressure turbine 16 and the intermediate pressure turbine 17, respectively.
- the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
- the compressor drum or compressor disk 26 and the blades 22 arranged thereon and the turbine rotor hub 27 and the turbine blades 24 arranged thereon rotate in operation around the engine axis 1.
- FIG. 1 shows a fairing 28 of a bypass channel 37 and the reference numeral 34 the already explained construction of the core engine.
- FIG. 2 shows a forward thrust position in oblique view in front, in which the panel 28th is closed to allow an undisturbed flow through the bypass channel. This state is also shown schematically in the lower half of FIG. 6. It can be seen in particular that a front, stationary portion 29 of the panel 28 forms the first part of the boundary of the bypass channel 37, while a rear portion 30 of the panel 28 is displaceable in the axial direction. This is apparent from a comparison of the upper half of the picture and the lower half of Fig. 6. Thus, Fig. 2 shows the forward thrust position, while Fig. 3 illustrates the thrust reversing position in which the rear portion 30 of the fairing 28 is axially displaced. This results in an annular free space 31, which is interrupted only by the not shown in detail range of a pylon for suspension of the aircraft gas turbine.
- FIGS. 4 and 5 show in rear perspective oblique view the illustration of Fig. 2 and 3, wherein the representation of the front portion 29 of the panel 28 has been omitted to make the deflecting elements 32 better visible.
- Fig. 4 forward thrust position
- the deflection elements 32 are arranged within the lining of the bypass channel 37 so that a flow through the bypass channel 37 is not hindered (lower half of FIG. 6).
- the individual deflecting elements 32 are moved in a circular arc-shaped path to the rear and inward.
- FIG. 4 and 5 shows that the deflecting elements 32 are at a distance from one another in the forward thrust position.
- the diverting elements 32 are approximated in the circumferential direction, so that the gap formed by the distance (FIG. 4) closes and the reversing elements 32 butt against each other at its trailing edge, as shown in FIG is.
- front and rear refer to the flow direction of the aircraft gas turbine, “front” corresponds to the inflow region, “rear” corresponds to the outlet region.
- FIG. 6 shows that the deflecting elements 32 comprise at their rear end region a blocking element 33 pointing radially inward, which is located in the Thrust reverser position (upper half of FIG. 6) against the lining 21 of the core engine 34 is applied.
- the rear portion 30 of the panel 28 has at its front end to a leading edge 38, which abuts in the thrust reversing position (upper half of FIG. 6) against the rear end portion of the deflecting elements 32 and leads to a complete closure in the axial rearward direction of the bypass channel 37 ,
- the deflecting elements 32 are formed like a lattice or cascade and comprise a multiplicity of flow-optimized guide elements 35.
- FIGS. 7 to 10 furthermore show rail elements 36, which are designed as telescopic rails and on which the deflecting elements 32 are mounted.
- the rail elements 36 are formed like a partial arc and designed to match rail elements 39 of the deflecting elements 32, so that the deflecting elements 32 are stored in a simple manner stable and precise.
- the deflecting elements 32 may be manufactured, for example, as castings or as composite parts.
- the inventive design results in the thrust reversing position tensile forces acting on the deflecting elements 32 and fix them in the thrust reverser position. Furthermore, a radial force component results, which contributes to a sealing engagement of the blocking elements 33 on the cladding 31. If one considers the individual webs of the cascade-like deflecting element 32, then a force component which acts radially inwards results, with respect to the forces acting in the flow, on the above-described contact pressure of the deflecting elements 32 in the radial direction inwardly and thus the sealing engagement of the blocking elements 33 causes. This effect is reinforced by the flow acting on the blocking elements 33 during their deflection, as can be seen from the upper part of FIG. 6. LIST OF REFERENCE NUMBERS
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102011008917A DE102011008917A1 (de) | 2011-01-19 | 2011-01-19 | Fluggasturbinenschubumkehrvorrichtung |
PCT/EP2012/000240 WO2012097995A1 (de) | 2011-01-19 | 2012-01-19 | Fluggasturbinenschubumkehrvorrichtung |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2665910A1 true EP2665910A1 (de) | 2013-11-27 |
EP2665910B1 EP2665910B1 (de) | 2016-03-30 |
Family
ID=45524512
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12700788.8A Active EP2665910B1 (de) | 2011-01-19 | 2012-01-19 | Fluggasturbinenschubumkehrvorrichtung |
Country Status (4)
Country | Link |
---|---|
US (1) | US9328694B2 (de) |
EP (1) | EP2665910B1 (de) |
DE (1) | DE102011008917A1 (de) |
WO (1) | WO2012097995A1 (de) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9016040B2 (en) | 2012-11-30 | 2015-04-28 | General Electric Company | Thrust reverser system with translating-rotating cascade and method of operation |
FR3010146B1 (fr) * | 2013-08-30 | 2015-12-18 | Aircelle Sa | Nacelle a dispositif d’inversion de poussee a grilles mobiles maintenues |
DE102013226767A1 (de) * | 2013-12-19 | 2015-07-09 | Liebherr-Aerospace Lindenberg Gmbh | Fluggasturbine mit einer Schubumkehrvorrichtung mit Kaskadenelementen und integriertem Zahnstangenantrieb |
DE102014210025A1 (de) | 2014-05-26 | 2015-12-17 | Rolls-Royce Deutschland Ltd & Co Kg | Schubumkehrkaskadenelement einer Fluggasturbine |
US10309343B2 (en) * | 2014-11-06 | 2019-06-04 | Rohr, Inc. | Split sleeve hidden door thrust reverser |
US9945324B2 (en) | 2014-11-06 | 2018-04-17 | Rohr, Inc. | Sleeve linkage for thrust reverser |
DE102015203219A1 (de) * | 2015-02-23 | 2016-08-25 | Rolls-Royce Deutschland Ltd & Co Kg | Triebwerksverkleidung einer Gasturbine mit Schubumkehrvorrichtung und im Querschnitt verstellbarer Ausströmdüse |
US10247136B2 (en) | 2015-12-03 | 2019-04-02 | General Electric Company | Thrust reverser system for a gas turbine engine |
FR3059299B1 (fr) * | 2016-11-30 | 2021-11-12 | Safran Nacelles | Nacelle de turboreacteur d’aeronef, ensemble propulsif et aeronef comportant une telle nacelle |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1027521B (de) * | 1954-12-23 | 1958-04-03 | Armstrong Siddeley Motors Ltd | Strahltriebwerk mit Mitteln zur Schubumkehr |
US3036431A (en) | 1959-09-08 | 1962-05-29 | Boeing Co | Thrust reverser for jet engines |
US3248878A (en) * | 1963-09-18 | 1966-05-03 | Gen Electric | Thrust deflector and reverser |
GB1052963A (de) | 1963-09-30 | |||
US3824784A (en) * | 1969-09-29 | 1974-07-23 | Secr Defence | Thrust deflectors for ducted fan gas turbine engines |
US3699682A (en) * | 1971-01-04 | 1972-10-24 | Mc Donnell Douglas Corp | Turbofan engine thrust reverser |
FR2162257B1 (de) | 1971-12-07 | 1975-02-07 | Snecma | |
US3981451A (en) * | 1975-11-17 | 1976-09-21 | Rohr Industries, Inc. | Fan cascade thrust reverser |
GB2189550A (en) | 1986-04-25 | 1987-10-28 | Rolls Royce | A gas turbine engine powerplant with flow control devices |
GB2196911B (en) | 1986-10-30 | 1990-03-14 | Rolls Royce Plc | Thrust reverser |
FR2634251B1 (fr) | 1988-07-18 | 1993-08-13 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a double flux equipe de bords de deviation mobiles |
US5039171A (en) * | 1989-08-18 | 1991-08-13 | Societe Anonyme Dite Hispano-Suiza | Multi-panel thrust reverser door |
FR2712929B1 (fr) | 1993-11-24 | 1995-12-29 | Hispano Suiza Sa | Inverseur de poussée de turboréacteur à double flux. |
FR2721977B1 (fr) | 1994-06-30 | 1996-08-02 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a double flux a obstacles lies au capot primaire |
FR2722534B1 (fr) | 1994-07-13 | 1996-08-14 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur double flux, a obstacles externes |
FR2804474B1 (fr) | 2000-01-27 | 2002-06-28 | Hispano Suiza Sa | Inverseur de poussee a grilles aubagees de deviation a structure arriere fixe |
GB0608985D0 (en) | 2006-05-06 | 2006-06-14 | Rolls Royce Plc | Aeroengine thrust reverser |
GB0616740D0 (en) | 2006-08-24 | 2006-10-04 | Short Brothers Plc | Aircraft engine thrust reverser |
US8109467B2 (en) * | 2009-04-24 | 2012-02-07 | United Technologies Corporation | Thrust reverser assembly with shaped drag links |
-
2011
- 2011-01-19 DE DE102011008917A patent/DE102011008917A1/de not_active Withdrawn
-
2012
- 2012-01-19 WO PCT/EP2012/000240 patent/WO2012097995A1/de active Application Filing
- 2012-01-19 EP EP12700788.8A patent/EP2665910B1/de active Active
- 2012-01-19 US US13/979,782 patent/US9328694B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2012097995A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE102011008917A1 (de) | 2012-07-19 |
WO2012097995A1 (de) | 2012-07-26 |
EP2665910B1 (de) | 2016-03-30 |
US9328694B2 (en) | 2016-05-03 |
US20130318945A1 (en) | 2013-12-05 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2665910B1 (de) | Fluggasturbinenschubumkehrvorrichtung | |
EP2628936B1 (de) | Fluggasturbinenschubumkehrvorrichtung | |
EP2960437B1 (de) | Leitschaufelvorrichtung für eine gasturbine sowie gasturbine mit einer solchen leitschaufelvorrichtung | |
DE60226288T2 (de) | Kaskadenförmige Schubumkehrvorrichtung | |
EP2714518B1 (de) | Fluggasturbinentriebwerk | |
EP3059431B1 (de) | Triebwerksverkleidung einer gasturbine mit schubumkehrvorrichtung und im querschnitt verstellbarer ausströmdüse | |
EP3306066B1 (de) | Turbofan-triebwerk für ein ziviles überschallflugzeug | |
WO2009030197A1 (de) | Mehrschichtiger abschirmungsring für einen flugantrieb | |
DE3632867A1 (de) | Mantelstrom-gasturbinentriebwerk | |
EP2835522B2 (de) | Vorrichtung und Verfahren zum Abblasen von Verdichterluft in einem Triebwerk | |
EP2543861B1 (de) | Fluggasturbine mit variabler Nebenstromdüse | |
EP3009683B1 (de) | Anordnung und verfahren zum abblasen von verdichterluft in einem triebwerk | |
DE102013206595B4 (de) | Strahltriebwerk | |
DE102013002192A1 (de) | Turbine für einen Abgasturbolader | |
EP3075661B1 (de) | Triebwerksverkleidung einer fluggasturbine | |
DE102011008918A1 (de) | Fluggasturbinenschubumkehrvorrichtung | |
EP3081797A1 (de) | Triebwerksverkleidung einer fluggasturbine | |
EP3387244A1 (de) | Fluggasturbine mit variabler austrittsdüse eines nebenstromkanals | |
WO2012097996A1 (de) | Fluggasturbinenschubumkehrvorrichtung | |
DE102011008525B4 (de) | Leitvorrichtung für eine Turbine sowie derartige Turbine eines Turboladers | |
EP3009648B1 (de) | Fluggasturbinenschubumkehrvorrichtung mit führungsschiene | |
DE102016100575A1 (de) | Schubumkehrvorrichtung einer Strömungsmaschine | |
DE102015206143A1 (de) | Vorrichtung zur Beeinflussung von Bodenwirbeln im Ansaugbereich einer Fluggasturbine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20130624 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
DAX | Request for extension of the european patent (deleted) | ||
17Q | First examination report despatched |
Effective date: 20150211 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R079 Ref document number: 502012006495 Country of ref document: DE Free format text: PREVIOUS MAIN CLASS: F02K0001720000 Ipc: F02K0003020000 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F02K 3/02 20060101AFI20150819BHEP Ipc: F02K 1/72 20060101ALI20150819BHEP |
|
INTG | Intention to grant announced |
Effective date: 20150909 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 785682 Country of ref document: AT Kind code of ref document: T Effective date: 20160415 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: GERMAN |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 502012006495 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160630 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160701 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160730 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160801 Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502012006495 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 6 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20170103 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170131 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170131 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170131 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170119 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 7 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20170131 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170119 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 785682 Country of ref document: AT Kind code of ref document: T Effective date: 20170119 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170119 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20120119 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CY Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160330 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20210128 Year of fee payment: 10 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20220119 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220119 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230124 Year of fee payment: 12 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230127 Year of fee payment: 12 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230528 |